In hypersonic flight, the prediction of aerodynamic heating and the construction of a proper thermal protection system (TPS) are significantly important. In this study, the method of a film cooling technique, which is already the state of the art in cooling of gas turbine engines, is proposed for a fully reusable and active TPS. Effectiveness of the film cooling scheme to reduce convective heating rates for a blunt-nosed spacecraft flying at Mach number 6.56 and 40 deg angle of attack is investigated numerically. The inflow boundary conditions used the standard values at an altitude of 30 km. The computational domain consists of infinite rows of film cooling holes on the bottom of a blunt-nosed slab. Laminar and several turbulent calculations have been performed and compared. The influence of blowing ratios on the film cooling effectiveness is investigated. The results exhibit that the film cooling technique could be an effective method for an active cooling of blunt-nosed bodies in hypersonic flows.
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e-mail: IbrahimH@alcor.concordia.ca
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December 2011
Technical Briefs
Numerical Study of Film Cooling Scheme on a Blunt-Nosed Body in Hypersonic Flow
Sung In Kim,
Sung In Kim
Department of Mechanical and Industrial Engineering,
Concordia University
, Montreal, QC, H3G 2W1, Canada
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Ibrahim Hassan
Ibrahim Hassan
Department of Mechanical and Industrial Engineering,
e-mail: IbrahimH@alcor.concordia.ca
Concordia University
, Montreal, QC, H3G 2W1, Canada
Search for other works by this author on:
Sung In Kim
Department of Mechanical and Industrial Engineering,
Concordia University
, Montreal, QC, H3G 2W1, Canada
Ibrahim Hassan
Department of Mechanical and Industrial Engineering,
Concordia University
, Montreal, QC, H3G 2W1, Canada
e-mail: IbrahimH@alcor.concordia.ca
J. Thermal Sci. Eng. Appl. Dec 2011, 3(4): 044501 (7 pages)
Published Online: October 13, 2011
Article history
Received:
December 27, 2010
Revised:
August 26, 2011
Online:
October 13, 2011
Published:
October 13, 2011
Citation
Kim, S. I., and Hassan, I. (October 13, 2011). "Numerical Study of Film Cooling Scheme on a Blunt-Nosed Body in Hypersonic Flow." ASME. J. Thermal Sci. Eng. Appl. December 2011; 3(4): 044501. https://doi.org/10.1115/1.4005052
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